| Summary: | 碩士 === 國防大學理工學院 === 兵器系統工程碩士班 === 104 === Ballistic missile re-entry except with the characteristics of high-speed maneuver, that can also change the flight path according to mission requirements, in order to improve the intercept accuracy and increase the survival ability of warheads and penetration ability. Therefore, designing a guidance law of air defense missiles have the ability to intercept maneuvering ballistic missiles, that is nowadays the important issues of the development of anti-ballistic missile system. In this study, Based on the extended Kalman filter (EKF) and input estimation (IE) method to deal with ballistic missile trajectory measurements by radar with noise, so as to get a more accurate estimation of the state and movement of ballistic missiles. Based on the trajectory estimator, using the method of proportional guidance and designing method of improved particle swarm optimization to build guidance law of anti-ballistic missile. With the above two guidance methods to simulate and compare with anti-ballistic missile tracking and interception performance of maneuvering and non-maneuvering ballistic missile. The simulation results show that performance of improved particle swarm optimization guidance (IPSOG) law is better than proportional navigation guidance (PNG) law in miss distance (MD), time-to-go (Tgo), average lateral acceleration and range interception. Improved particle swarm optimization guidance law can effectively improve the probability of intercepting maneuvering ballistic missiles. This study results expect to contribute to the guidance law of future development anti-ballistic missiles that effectively enhance the ability of ballistic missile defense.
|
|---|
